Author/Authors :
Lin, A. Q College of Power and Energy Engineering - Harbin Engineering University, Harbin, Heilongjiang Province, China , Zhou, J AECC Sichuan Gas Turbine Establishment, Sichuan Province, China , Tian, X. J AECC Sichuan Gas Turbine Establishment, Sichuan Province, China , Zheng, Q College of Power and Energy Engineering - Harbin Engineering University, Harbin, Heilongjiang Province, China , Zhang, H College of Power and Energy Engineering - Harbin Engineering University, Harbin, Heilongjiang Province, China
Abstract :
Flow characteristics inside the compressor are of great importance for aeroengine performance under the high
adverse pressure gradient. To meet the need for quick performance estimation, the numerical simulation is a
meaningful investigation method to predict the similarity flow characteristics of aeroengine compressor at
high Mach flight. Thus, this paper aims to satisfy the accuracy of compressor flow field at high altitude based
on the similarity criterion. The accuracy for solution results by the application of the similarity criterion and
the derivation of compressor boundary conditions is verified with the experimental data. Then, the parametric
definitions of air intake are put forward to get the inlet boundary conditions of compressor. The comparative
simulation results are conducted between similarity and prototype flow fields at design boundary conditions.
The results show that among the most important dimensionless criterion is Mach number at high-speed flow,
so the same equivalent mass flow and equivalent speed are recommended. In addition, the flow characteristics
of the compressor at high altitude and high Mach number have a good similarity. Consequently, it can extend
to further study compressor performance of aeroengine at different flight altitudes and Mach numbers.
Keywords :
Parametric definition , Similarity criterion , High Mach , Aeroengine compressor
